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Research Papers: Gas Turbines: Ceramics

Durability of Oxide/Oxide Ceramic Matrix Composites in Gas Turbine Combustors

[+] Author and Article Information
Mark van Roode

Mark van Roode & Associates,
San Diego, CA 92110

Arun K. Bhattacharya

Solar Turbines Incorporated,
San Diego, CA 92101

Contributed by the International Gas Turbine Institute of ASME for publication in the Journal of Engineering for Gas Turbines and Power. Manuscript received October 15, 2012; final manuscript received October 17, 2012; published online April 23, 2013. Assoc. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 135(5), 051301 (Apr 23, 2013) (9 pages) Paper No: GTP-12-1404; doi: 10.1115/1.4007978 History: Received October 15, 2012; Revised October 17, 2012

An integrated creep rupture strength degradation and water vapor degradation model for gas turbine oxide-based ceramic matrix composite (CMC) combustor liners was expanded with heat transfer computations to establish the maximum turbine rotor inlet temperature (TRIT) for gas turbines with 10:1 pressure ratio. Recession rates and average CMC operating temperatures were calculated for an existing baseline N720/A (N720/Al2O3) CMC combustor liner system with and without protective Al2O3 friable graded insulation (FGI) for 30,000-h liner service life. The potential for increasing TRIT by Y3Al5O12 (YAG) substitution for the fiber, matrix, and FGI constituents of the CMC system was explored, because of the known superior creep and water vapor degradation resistance of YAG compared to Al2O3. It was predicted that uncoated N720/A can be used as a combustor liner material up to a TRIT of ∼1200  °C, offering no TRIT advantage over a conventional metal + thermal barrier coating (TBC) combustor liner. A similar conclusion was previously reached for a SiC/SiC CMC liner with barium strontium aluminum silicate (BSAS)-type environmental barrier coating (EBC). The existing N720/A + Al2O3 FGI combustor liner system can be used at a maximum TRIT of ∼1350  °C, a TRIT increase over metal + TBC, and uncoated N720/A of ∼150  °C. Replacing the Al2O3 with YAG is predicted to increase the maximum allowable TRIT. Substitution of the fiber or matrix in N720/A increases TRIT by ∼100  °C. A YAG FGI improves the TRIT of the N720/A + Al2O3 FGI by ∼50  °C, enabling a TRIT of ∼1400 °C, similar to that predicted for SiC/SiC CMCs with protective rare earth monosilicate EBCs.

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Figures

Grahic Jump Location
Fig. 1

Combustor liner surface recession schematic for hybrid oxide CMC + FGI [17]

Grahic Jump Location
Fig. 2

Maximum stress versus UUT for CMC systems with/without Al2O3- and YAG-based FGIs (PR 10:1) for 30,000 h of exposure

Grahic Jump Location
Fig. 3

Schematic of combustor liner cooling

Grahic Jump Location
Fig. 4

Average N720/A temperature over 30,000 h versus TRIT for various CMC thicknesses–UUT 1070  °C

Grahic Jump Location
Fig. 5

Average N720/YAG temperature over 30,000 h versus TRIT for various CMC thicknesses–UUT 1070  °C

Grahic Jump Location
Fig. 6

Average YAG/A temperature over 30,000 h versus TRIT for various CMC thicknesses–UUT 1120 °C

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Fig. 7

Average YAG/YAG temperature over 30,000 h versus TRIT for various CMC thicknesses–UUT 1140  °C

Grahic Jump Location
Fig. 8

Average N720/A + Al2O3 FGI temperature over 30,000 h versus TRIT for various CMC and FGI thicknesses–UUT 1140  °C

Grahic Jump Location
Fig. 9

Average N720/A + YAG FGI temperature over 30,000 h versus TRIT–UUT 1140  °C YAG FGI thickness: 4 mm

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